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GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GRUMMAN K-2 AIRFOIL (k2-il)
Reynolds number: 500,000
Max Cl/Cd: 52.26 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k2-il-500000-n5.txt
Download as CSV file: xf-k2-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GRUMMAN K-2 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.9369   0.07067   0.06723  -0.0479   1.0000   0.0118
 -13.250  -0.9689   0.06148   0.05780  -0.0536   1.0000   0.0118
 -13.000  -0.9935   0.05505   0.05116  -0.0563   1.0000   0.0118
 -12.750  -1.0133   0.05012   0.04602  -0.0572   1.0000   0.0118
 -12.500  -1.0291   0.04619   0.04188  -0.0570   1.0000   0.0118
 -12.250  -1.0419   0.04293   0.03843  -0.0558   1.0000   0.0118
 -12.000  -1.0518   0.04021   0.03553  -0.0541   1.0000   0.0119
 -11.750  -1.0595   0.03791   0.03304  -0.0518   1.0000   0.0119
 -11.500  -1.0655   0.03594   0.03091  -0.0491   1.0000   0.0120
 -11.250  -1.0707   0.03423   0.02905  -0.0460   1.0000   0.0121
 -11.000  -1.0759   0.03278   0.02745  -0.0424   1.0000   0.0121
 -10.750  -1.0825   0.03155   0.02610  -0.0382   1.0000   0.0122
 -10.500  -1.0827   0.03027   0.02468  -0.0350   1.0000   0.0122
 -10.250  -1.0770   0.02896   0.02323  -0.0326   1.0000   0.0123
 -10.000  -1.0682   0.02775   0.02188  -0.0307   1.0000   0.0124
  -9.750  -1.0569   0.02663   0.02062  -0.0290   1.0000   0.0124
  -9.500  -1.0456   0.02533   0.01922  -0.0272   1.0000   0.0126
  -9.250  -1.0316   0.02429   0.01808  -0.0257   1.0000   0.0127
  -9.000  -1.0077   0.02329   0.01700  -0.0262   0.9992   0.0128
  -8.750  -0.9832   0.02241   0.01605  -0.0265   0.9983   0.0130
  -8.500  -0.9577   0.02161   0.01518  -0.0270   0.9973   0.0132
  -8.250  -0.9313   0.02085   0.01435  -0.0276   0.9963   0.0134
  -8.000  -0.9043   0.02011   0.01355  -0.0282   0.9954   0.0136
  -7.750  -0.8771   0.01941   0.01279  -0.0288   0.9947   0.0139
  -7.250  -0.8239   0.01810   0.01135  -0.0297   0.9930   0.0144
  -7.000  -0.7977   0.01749   0.01068  -0.0299   0.9919   0.0148
  -6.750  -0.7708   0.01693   0.01005  -0.0303   0.9909   0.0151
  -6.500  -0.7432   0.01635   0.00945  -0.0308   0.9898   0.0155
  -6.250  -0.7147   0.01586   0.00895  -0.0315   0.9888   0.0161
  -6.000  -0.6852   0.01545   0.00853  -0.0323   0.9877   0.0167
  -5.750  -0.6552   0.01504   0.00810  -0.0332   0.9868   0.0175
  -5.500  -0.6244   0.01463   0.00766  -0.0342   0.9859   0.0182
  -5.250  -0.5931   0.01418   0.00720  -0.0354   0.9851   0.0190
  -5.000  -0.5613   0.01381   0.00684  -0.0366   0.9844   0.0200
  -4.750  -0.5294   0.01349   0.00651  -0.0378   0.9838   0.0212
  -4.500  -0.5009   0.01317   0.00617  -0.0382   0.9826   0.0224
  -4.250  -0.4732   0.01285   0.00587  -0.0384   0.9811   0.0241
  -4.000  -0.4438   0.01260   0.00562  -0.0390   0.9796   0.0261
  -3.750  -0.4134   0.01229   0.00535  -0.0398   0.9784   0.0288
  -3.500  -0.3826   0.01204   0.00512  -0.0407   0.9773   0.0318
  -3.250  -0.3514   0.01181   0.00491  -0.0416   0.9763   0.0358
  -3.000  -0.3198   0.01157   0.00472  -0.0427   0.9755   0.0420
  -2.750  -0.2875   0.01131   0.00453  -0.0439   0.9746   0.0516
  -2.500  -0.2541   0.01100   0.00434  -0.0454   0.9739   0.0710
  -2.250  -0.2193   0.01055   0.00413  -0.0473   0.9732   0.1202
  -2.000  -0.1831   0.00990   0.00390  -0.0499   0.9729   0.2158
  -1.750  -0.1460   0.00925   0.00369  -0.0527   0.9728   0.3224
  -1.500  -0.1057   0.00843   0.00345  -0.0565   0.9732   0.4630
  -1.250  -0.0646   0.00774   0.00340  -0.0601   0.9739   0.6169
  -1.000  -0.0315   0.00769   0.00366  -0.0610   0.9731   0.6936
  -0.750   0.0012   0.00772   0.00373  -0.0618   0.9705   0.7160
  -0.500   0.0363   0.00754   0.00358  -0.0629   0.9626   0.7237
  -0.250   0.0753   0.00725   0.00328  -0.0647   0.9522   0.7306
   0.000   0.1108   0.00697   0.00299  -0.0658   0.9396   0.7362
   0.250   0.1425   0.00683   0.00287  -0.0661   0.9227   0.7422
   0.500   0.1832   0.00669   0.00269  -0.0684   0.9021   0.7508
   0.750   0.2272   0.00660   0.00252  -0.0713   0.8565   0.7546
   1.000   0.2514   0.00732   0.00249  -0.0699   0.6822   0.7573
   1.250   0.2701   0.00807   0.00270  -0.0679   0.5520   0.7602
   1.500   0.2931   0.00866   0.00285  -0.0670   0.4444   0.7631
   1.750   0.3179   0.00922   0.00299  -0.0666   0.3411   0.7660
   2.000   0.3448   0.00957   0.00311  -0.0665   0.2843   0.7684
   2.250   0.3705   0.00992   0.00326  -0.0660   0.2331   0.7700
   2.500   0.3965   0.01027   0.00344  -0.0656   0.1866   0.7717
   2.750   0.4226   0.01062   0.00361  -0.0653   0.1459   0.7735
   3.000   0.4492   0.01096   0.00379  -0.0650   0.1137   0.7754
   3.250   0.4764   0.01123   0.00396  -0.0649   0.0929   0.7774
   3.500   0.5041   0.01147   0.00413  -0.0649   0.0792   0.7796
   3.750   0.5320   0.01172   0.00430  -0.0649   0.0652   0.7817
   4.250   0.5866   0.01243   0.00478  -0.0648   0.0288   0.7855
   4.500   0.6129   0.01276   0.00509  -0.0644   0.0216   0.7868
   4.750   0.6393   0.01308   0.00541  -0.0640   0.0173   0.7881
   5.000   0.6657   0.01341   0.00574  -0.0637   0.0151   0.7895
   5.250   0.6922   0.01375   0.00609  -0.0633   0.0138   0.7911
   5.500   0.7186   0.01413   0.00648  -0.0630   0.0129   0.7928
   5.750   0.7453   0.01449   0.00688  -0.0627   0.0122   0.7944
   6.000   0.7720   0.01486   0.00729  -0.0625   0.0116   0.7960
   6.250   0.7986   0.01528   0.00773  -0.0623   0.0111   0.7978
   6.500   0.8248   0.01580   0.00827  -0.0620   0.0106   0.7998
   6.750   0.8512   0.01633   0.00883  -0.0618   0.0103   0.8015
   7.000   0.8767   0.01682   0.00938  -0.0613   0.0101   0.8028
   7.250   0.9014   0.01736   0.01000  -0.0607   0.0098   0.8039
   7.500   0.9258   0.01795   0.01066  -0.0600   0.0096   0.8050
   7.750   0.9498   0.01858   0.01136  -0.0593   0.0094   0.8063
   8.000   0.9735   0.01925   0.01211  -0.0586   0.0092   0.8078
   8.250   0.9971   0.01996   0.01290  -0.0578   0.0090   0.8093
   8.500   1.0204   0.02070   0.01372  -0.0571   0.0089   0.8108
   8.750   1.0434   0.02150   0.01460  -0.0563   0.0088   0.8123
   9.000   1.0661   0.02235   0.01555  -0.0555   0.0087   0.8138
   9.250   1.0883   0.02325   0.01654  -0.0547   0.0086   0.8153
   9.500   1.1101   0.02418   0.01757  -0.0538   0.0085   0.8170
   9.750   1.1312   0.02523   0.01872  -0.0529   0.0084   0.8187
  10.000   1.1498   0.02645   0.02007  -0.0516   0.0082   0.8200
  10.250   1.1653   0.02808   0.02190  -0.0499   0.0081   0.8211
  10.500   1.1830   0.02926   0.02325  -0.0485   0.0080   0.8222
  10.750   1.1996   0.03051   0.02470  -0.0469   0.0080   0.8234
  11.000   1.2144   0.03194   0.02633  -0.0452   0.0079   0.8247
  11.250   1.2267   0.03357   0.02819  -0.0432   0.0079   0.8261
  11.500   1.2365   0.03537   0.03021  -0.0410   0.0078   0.8277
  11.750   1.2425   0.03743   0.03253  -0.0384   0.0078   0.8295
  12.000   1.2447   0.03968   0.03504  -0.0355   0.0078   0.8313
  12.250   1.2394   0.04193   0.03752  -0.0316   0.0077   0.8330
  12.500   1.2315   0.04451   0.04032  -0.0281   0.0077   0.8347
  12.750   1.2177   0.04771   0.04377  -0.0248   0.0077   0.8361
  13.000   1.2019   0.05131   0.04761  -0.0225   0.0077   0.8373
  13.250   1.1801   0.05618   0.05274  -0.0219   0.0077   0.8385
  13.500   1.1546   0.06297   0.05978  -0.0248   0.0077   0.8399
  13.750   1.1176   0.07769   0.07483  -0.0380   0.0078   0.8411
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